To reconcile flutter characteristic improvement of a wing including a constitutional member used in an aircraft, and formed of a composite material, with reduction of manufacturing cost.SOLUTION: In a wing 10, an upper outer plate 11 which is a constitutional member is classified into a plurality of areas 20 along the surface. The plurality of areas 20 includes a first area 201 formed of a highly-strong type composite material, and a second area 202 formed of a highly-elastic type composite material having higher stiffness than the highly-strong type. The first area 201 includes areas 21, 22 on the most wing-tip 10b side among the plurality of areas 20, and the second area 202 includes an area 23 on the most wing-tip 10b side and on the rear edge 10d side among the plurality of areas 20.SELECTED DRAWING: Figure 3
【課題】航空機に用いられ、複合材で形成された構成部材を備える翼のフラッタ特性向上と製造コスト低減の両立を図る。【解決手段】翼10において、構成部材である上方外板11は、表面に沿って複数の領域20に区分される。複数の領域20は、高強度タイプの複合材で形成された第1領域201と、高強度タイプより剛性が大きい高弾性タイプの複合材で形成された第2領域202とを含む。第1領域201は、複数の領域20のうち最も翼端10b側の領域21、22を含み、第2領域202は、複数の領域20のうち最も翼端10b側かつ後縁10d側の領域23を含む。【選択図】図3
WING, AND DESIGN METHOD OF WING
翼および翼の設計方法
09.05.2019
Patent
Elektronische Ressource
Japanisch
IPC: | B64C AEROPLANES , Flugzeuge |
Wiley | 2025
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